Turbine-nozzle.



J. F. METTEN.

TURBINE NOZZLE.

APPLICATION mu) JULY 3.1914.

Patented; Jan. 30, 1917.

3 SHEETS-SHEET l.

FJL

J. F. METTEN.

TURBINE NOZZLE.

APPLICATION FILED JULY 3. I914.

131 mm Patented Jan. 30,1917.

3 SHEETS-SHEET 2.

J. F. METTEN.

TURBINE NOZZLE.

APPLICATION FILED JULY 3.1914.

Patented Jan. 0 917.

3 SHEETSS 3.

F.5, F. S A

w vtnwoeo lit) JOHN METTEN, DI PHILADELPHIA, PENNSYLVANIA, ASSIGNOR TO THE WILLIAM CHAMP & SONS SHIP & ENGINE BUILDING COMPANY, A. CORPORATION GI PENN- srnvra.

TURBINE-NOZZLE.

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To all whom it may concern:

Be it known that I, JOHN F. Mnrrnn, a citizen of the United States, residing at Philadelphia, in the county of Philadelphia and State of Pennsylvania, have invented certain new and useful Improvements 1n Turbine-Nozzles, of which the following is a full, clear, and exact specificatlon.

This invention relates to steam turbines, and has particular reference to multi-stage turbines of the impulse type, wherein the several stages are separated by diaphragms having passages or nozzles for passing the steam into the successive stages. These diaphragms, especially where there is-full peripheral admission of steam, as in marine turbines, have been built heretofore 1n such manner that the strain due to the steam pressure is transmitted to the casing through the nozzle or blade structure itself. This requires that the nozzle structure be constructed strong enough to transmit the total axial pressure on the diaphragm to the'casing.

It is the object of this invention to relieve the nozzle structure of this strain by making it in segments separate from the diaphragm itself, or the locking ring or other part which is interposed between the diaphragm and the casing and which transmits the strain. are realized both, in the original construction of the turbine, and in case it is later desired to inspect or repair the nozzle blading. In manufacture, the advantages reside in constructing the nozzle blading separately from the diaphragm, thereby avoiding strains in the blading, and also permitting the design and material of the blading to be such as not to corrode or wear,

and of best efficiency. In case of inspection or repair, any nozzle ring segment can be removed and replaced without dismantling the entire structure.

In the preferred form herein shown. the diaphragm consists of a disk havlng a grooved rim secured to its periphery, and between the diaphragm and the casing is interposed a segmental nozzle carryingrin to which latter ring the segmental nozz e rings and blades are separably attached. Thereby. the nozzle rings and blades are not subjected to the axial strain due to the total pressure on the diaphragm, they can be better designed of more suitable material,

Specification of Letters Patent.

Therebv, a number of advantages and in case of damage new blades can be easily supplied. As herein shown, the ring oarrylng the separable nozzle ring segments and blades is slidable between the diaphragm and the casing, and to readily permit this, the diaphragm and easing grooves, or either of them, are provided with nonrustmg composition liners, so that the lower rings can he slid around in the casing when the top is removed.

The invention is illustrated in the accompanying drawings, wherein- Figure 1 is an elevation, partly in section, of one of the removable nozzle carrymg rlngs; Fig. 2 is a longitudinal section; Fig. 3 is a detail on an enlarged scale; Fig. 4 1s a perspective view of one of the blades; and Figs. 5 and 6 are detail views on an enlarged scale of the nozzle carrying rings. A represents a casing containing the shaft 18. to which are secured the wheels C, each of which carries two or more rows of blades E, Between these rows of blades E are stationary blades Ur fixed to the casing. Between successive wheels C are stationary diaphragms H, each of which comprises a central'packing ring I attached to the cen ter of the disk H and a peripheral ring K overlying the ring I and attached to disk H on the opposite side, so as to reduce the overall length of the turbine. The ring is provided with a circumferential oove L. and the casing A has an internal circumferential groove M in which grooves channel'liners N. O, respectivelv of non-rusting metal are secured as by screws P. As will be seen, these grooves are comprised between parallel radial planes, and overlie each other so as to receive the segments of a slidable nozzle carrving ring Q. The segments of this ring Q each consist of separated bridge pieces R, between which the steam passes to the nozzles, together with internallv projecting tongues S on which tongues inner and outer blade carrying segments T, U slide. The bridge pieces R are made of sufficient strength to transmit the entire steam pressure on the diaphragm directly to the casing for the purpose of relieving the nozzle structure thereof. This not only permits the nozzle structure to be relieved of manufacturing strains, as example where the nozzle blades are cast in their" supporting structure. but also permits a greater freedom of design of the nozzles for , Patented Jan. 3d, ilhf't. Application filed July t, 19%. Serial Ito. tttfltl. I

themselves, both as to choice of material and their number, shape, proportions, etc. The nozzle blades V are shown in Fig. 4, as having top and bottom projections W which pass through holes in the rings T, U, and the projections may be headed over or riveted to the rings T, U. The segmental rings T, U, together with the blades V therefore constitute the nozzle segments, which can be successively slid in position on the tongues S of the nozzle carrying rings Q. The rings T, U are provided with inner shoulders as Z which bear against the tongues S, and when all of the nozzle ring segments have been assembled in one-half of the casing, or any other segment thereof, they can be fastened therein by riveting over the corners X on the beveled corners of the tongues S. The segments of the nozzle carrying rings Q are fastened in position by screws Y tapped into the casing, which screws become accessible when a portion of the casing is removed.

The nozzle carrying ring Q with bridges R is preferably made of steel, while the nozzle structure comprising the segmental rings T, U, with or without blades V, is preferably made of drawn bronze. The liners N, 0, may also be of bronze. This material is not subject to corrosion and weakening when subjected to the effect of high pressure steam moving at high velocity, and furthermore it can be accurately finished to the desired shape and dimensions. Thus the danger of broken blades is avoided, and the nozzles do not change in shape and design from corrosion, as happens when they are built of steel. As the nozzle structure is assembled without casting the parts together, obj ectionable stresses are not developed due to the pouring of hot metal, and every part can be made alike and examined before being inserted in the turbine, so that there will not be any loose blades or weak connections. This also permits the nozzle ing thickness, best form of the nozzle,

blades to be of varywhich adapts them to give the steam passage at all parts of which is especially desirable in impulse turbines which effect a major portion of the steam expansion in the stationary nozzles.

The present invention is also advantageous in case of necessitating inspecting or repairing a nozzle section or sections. When the casing is removed, or the nozzle carrying ring slid around in the lower half of the easing, the damaged nozzle blades can be removed by cutting off the blades from between the segmental rings, permitting the rings to be removed between the bridges in the carrying rings and then a new section can be inserted. If a section of nozzle blading to be removed lay directly in front of one of the bridges it would be necessary to cut out the nozzle blading far enough to one side or the other of the bridge to permit of the pieces being removed, and then two new short sections could be inserted. By this invention it is comparatively easy to cut Wherever desired and fit short pieces in to fill the gap, because even short sections when inserted would be equal in strength to the remainder of the nozzle ring, the ends of the containing ring being fitted close between the ends of the original section and the blades of the new short section being riveted in the same manner as on the original long section. The invention is especially applicable where full peripheral admission is employed, but it will be seen that blank sections could be inserted in the nozzle carrying rings if desired, so as to give only partial admission.

This application is a continuation in part of my application, Serial No. 780,682, filed July 23, 1913.

It will be understood that the particular construction herein shown is but one example of the manner in which the invention may be carried out, and that various modifications and changes may be made without departing from the scope of the appended claims.

Having thus described my invention, I declare that what I claim as new and desire to secure by Letters Patent is:

1. In a turbine, the combination with a casing, of a diaphragm, a separate nozzle carrying element engaging the casing and the diaphragm to lock the latter, and a separate nozzle structure mounted in said nozzle carrying element.

2. In a turbine, the combination with a casing, of a diaphragm, a separate nozzle carrying element slidably engaging the casing and the diaphragm to lock the latter, and a separate nozzle structure mounted in said nozzle carrying element.

3. In a turbine, the combination with a casing, of a diaphragm, a divided nozzle carrying ring slidably mounted between the casing and the diaphragm, and a segmental nozzle structure mounted in said ring.

4. In a turbine, the combination with a casing, of a diaphragm, a nozzle carrying ring slidably interlocking with both the easing and the diaphragm whereby the nozzle ring holds the diaphragm against displacement, and a nozzle structure comprising concentric rings and radial blades carried by said ring.

5. In a turbine, the combination with a casing around its inner surface, of a diaphragm, a segmental nozzle carrying ring formed to slidably interlock with the diaphragm and the grooved casing to hold the diaphragm in position and be slidably removable independently of the diaphragm. and a segmental nozzle structure mounted in said ring.

6. In a turbine, the combination with a casing having a removable section, of a diaphragm, a segmental nozzle carrying ring slidably interlocking the casing and the diaphragm whereby a segment within the easing can be pushed around and removed through an open portion of the casing, and a series of nozzle segments slidably inserted in said ring whereby a nozzle segment can be removed independently of the others.

In a turbine, the combination wlth a diaphragm, of a separate nozzle carrying ring segment interlocking therewith on its periphery, and a nozzle structure removably mounted in said ring and interlocklng therewith by a tongue and groove connection.

8. In a turbine, the combination with a diaphragm, of a nozzle carrying ring segment interlocking with said diaphragm, and a nozzle structure removably mounted in said ring and interlocking therewith.

9. In a turbine, the combination with a casing, of a diaphragm, a removable nozzle carrying segi-rient betweenthe casing and the diaphragm, said segment being capable of removal without removing the diaphragm, and a nozzle structure removably mounted in and interlocking with said segment.

10. In a turbine, the combination with a casing, of a shaft therein, a diaphragm encircling said shaft, said casing being d1- vided on a longitudinal plane through the shaft, a nozzle carrying ring separable from the diaphragm and separably fitted to the casing, said ring being divided into sectlons, removable tastenings for securing said ring sections to the casing sections, and a nozzle structure removably mounted in said nozzle rin 1%. In a turbine, the combination with a casing, of a shaft therein, a diaphragm encircling said shaft, said casing being divided on a longitudinal plane through the shaft, said diaphragm comprising a nozzle carrying ring divided into a plurality of segments and slidably interlocking the easing and the diaphragm, and a nozzle structure divided into a plurality of segments, said nozzle structure being slidable in said nozzle ring.

12. In a turbine, the combination with a sectional casing and a diaphragm, of a nozzle carrying ring segment fastened to and removable with a casing section, a second nozzle carrying ring segment slidably removable independently of the remainder of the casing and the diaphragm and a nozzle structure slidably mounted in said nozzle carrying ring.

13. In a turbine, the combination with a sectional casing, of a segmental nozzle carrying ring having separated bridges and fastened between the casing and the diaphragm, and a nozzle structure mounted in said nozzle ring at one side of sald bridges.

14. In a turbine, the combination with a casing, of a built-up diaphragm comprising a hub, a dished disk carried by said hub, a nozzle containing ring segment removably interposed between said disk and the casing, and a separate nozzle structure comprising nozzle blades, mounted in said segment.

15. In a turbine, the combination with a casing, of a diaphragm of less diameter than the casing, a nozzle structure container be tween and mechanically connecting said diaphragm with said casing, and a nozzle structure removably mounted in said interposed container.

16. In a turbine, the combination with a casing, of a diaphragm of less diameter than said casing, a nozzle carrying structure comprising an apertured bridged ring connecting the diaphragm and the casing, and removable nozzles in said ring.

17. In a turbine, the combination with a casing, of a diaphragm, a nozzle structure container mechanically connected with said diaphragm and said casing, and a nozzle structure removably mounted in said container, said nozzle structure comprising blade holding segments and nozzle blades secured between said segments.

18. The combination with a casing, of a diaphragm, a segmental nozzle container mechanically connecting said diaphragm with said casing, said container comprising inner and outer segments secured together by bridges or posts, between which posts steam may pass, and a nozzle structure slidable in said container, said nozzle structure comprising blade holding segments and nozzle blades secured between said segments.

19. The combination with a casing, of a diaphragm, a segmental nozzle container mechanically connecting said diaphragm with said casing, said container comprising inner and outer segments secured together by bridges or posts, between which posts steam may pass, and a nozzle structure slid ably mounted in said container, said nozzle structure comprising blade holding se cuts and nozzle blades secured between said segments, the material of said container being of one kind and the material of said nozzle structure being of a less corrodible material.

20. In a turbine, the combination with a casing having an internal projection, of a diaphragm having a peripheral projection spaced Within said casing projection, a connecting ring removably lnterlocking with said projections to mechanically connect said casing and said diaphragm, said connecting ring having a steam passage, and nozzle blades mounted on said connecting ring in said steam passage.

21. In a turbine, the combination with a nozzle support comprising spaced concentric rings and bridge pieces, of a plurality of spaced concentric rings carried thereby, and

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a plurality of blades between and interlocked with said latter rings.

22. In a turbine, the combination with a nozzle support comprising spaced concentric rings and bridge pieces, of a plurality of spaged concentric rings carried thereby, and a plurality of blades between and interlocked with said latter rings, said rings and blades being slidably separable as a unit from said support.

23. In a turbine, a nozzle element comprising spaced perforated segments, and blades between said segments having shanks extending through said perforations and headed over to fasten said blades and segments rigidly together.

24. In a turbine, a nozzle element comprising spaced perforated segments, blades between said segments having shanks extending through said perforations and headed over to fasten said blades and segments rigidly together, and a segmental annular support carrying said nozzle element.

25. In a turbine, a steel nozzle support, and composition ring segments connected by composition blades, slidable in said support.

26. In a turbine, a casing, a diaphragm,

a noncorroding liner thereon, a nozzle support slidably engaging said liner, and means transmitting strain from. the diaphragm to the casing.

27. In a turbine, a casing having a noncorroding liner, a diaphragm having a noncorroding liner, and a nozzle support slidably engaging said liner.

28. In a turbine, a nozzle element comprising concentric supporting segments, blade carrying segments adapted to be headed to engage said concentric segments, and blades carried by said segments. 7

29. In a turbine, a nozzle element comprising a support, a blade carrying segment having a shoulder engaging said support to oppose movement in one direction and headed engagement with said support to oppose movement in the opposite direction, and blades carried by said segment.

In testimony whereof I afiix my signature, in presence of two witnesses.

JOHN F. METTEN.

Witnesses:

JAMES H. KURTZ, J. H. MCMASTER. 

